变弹翼导弹动力学控制及仿真  

Dynamics and Control of Missile with Morphing Wings

作　　者：张天翼[1] 郭建国[1] 周军[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,陕西西安710072

出　　处：《计算机仿真》2011年第2期39-42,共4页Computer Simulation

基　　金：航天支撑基金(N8XW0001);西工大基础研究基金(JC201024)

摘　　要：研究飞行器优化控制问题,常规导弹由于弹翼固定使得其飞行性能单一。为了提高整个导弹的作战效率,采用变弹翼技术的导弹却能够实现低能耗优化飞行。由于变弹翼导弹的动力学模型与控制特性在飞行过程中弹翼的运动变得复杂化。提出弹翼采用较常见的"×"字形,针对四个变弹翼导弹建立相关气动特性,包含弹翼运动的全弹动力学方程。根据小扰动法与系数"冻结"法,采用全弹三通道数学模型。通过仿真结果表明,设计的自动驾驶仪能够抑制气动参数变化的影响,满足导弹控制性能指标要求,各项指标表明变弹翼导弹的作战效率可以得到提高。The performance of general missile is of singleness because of its fixed wings,while the missile with morphing wings can have the ability of multi-mission flight,which finally can improve the efficiency of the whole missile.By considering the interaction between the motion of the wings and the body,the multi-body dynamic model for the whole missile is given.For the missile with four morphing wings,the configuration of wing implies familiar furcated shape.The simple three-channel mathematical models are obtained with linear processing.The autopilot designs are finished by using the variable structure control theory.The results of the simulation shows that the controller meets the need of performance of the control system,and each index indicates that the efficiency of the whole missile can indeed improved.

关 键 词：变弹翼 导弹 动力学 变结构控制 

分 类 号：TJ393[兵器科学与技术—火炮、自动武器与弹药工程]